Product overview
The Mugin GV400 Flight Platform combines a moulded carbon fiber composite airframe, a 4 m wingspan and an H-tail with electric vertical lift and a separate gasoline engine for fixed-wing cruise. This architecture supports deployment where a runway is unavailable. Overall dimensions are approximately 4000 × 2021 × 701 mm, with 122 dm² of wing area. The fuselage provides approximately 1017 × 221 × 216 mm of internal space, shared between installed flight systems and project equipment; mounting requirements and the final layout determine payload fit.
The aircraft includes integrated propulsion, flight control, power and actuation systems. Mission payloads, communication links and ground control equipment are selected for each project, with supplied equipment defined in the final quotation. Maximum take-off weight is 25 kg and maximum payload is 4 kg. Reference endurance reaches five hours without payload, 4.5 hours with 2 kg and 5 L of fuel, or two hours with 4 kg and 2.5 L. Configuration, fuel load and operating conditions affect performance, while communication range depends on the selected data link.
Specifications
| Specification | Value & conditions |
|---|---|
| Product | Mugin GV400 Flight Platform; complete VTOL aircraft |
| Overall dimensions | Approx. 4000 × 2021 × 701 mmReference dimensions. |
| Wingspan and tail | 4 m wingspan; H-tail layout |
| Fuselage internal dimensions | Approx. 1017 × 221 × 216 mmReference dimensions; usable internal space depends on installed flight systems and equipment layout. |
| Wing area | 122 dm² |
| Primary structure | Carbon fiber composite |
| Propulsion | Gasoline cruise + electric VTOL |
| Fuel tank capacity | 5 LReference configuration. |
| Maximum take-off weight | 25 kg |
| Maximum payload | 4 kg |
| Maximum speed | 30 m/sPerformance varies with aircraft configuration, payload, fuel load and operating conditions. |
| Cruise speed | 21–24 m/sReference fixed-wing cruise; performance varies with aircraft configuration, payload, fuel load and operating conditions. |
| Stall speed | 18 m/sPerformance varies with aircraft configuration, payload, fuel load and operating conditions. |
| Maximum reference endurance | Up to 5 hoursNo payload; endurance varies with payload, fuel load and operating conditions. |
| Flight range | 300 kmReference; performance varies with aircraft configuration, payload, fuel load and operating conditions. |
| Wind resistance | VTOL Level 4 / Fixed-wing Level 6VTOL and fixed-wing flight modes respectively; performance varies with aircraft configuration, payload, fuel load and operating conditions. |
| Reference endurance with 2 kg payload | 4.5 hours2 kg payload carrying 5 L of fuel; actual endurance depends on final configuration and operating conditions. |
| Reference endurance with 4 kg payload | 2 hoursMaximum 4 kg payload carrying 2.5 L of fuel; actual endurance depends on final configuration and operating conditions. |
| Integrated systems | Propulsion, flight control, power and actuation systems |
| Mission and ground equipment | Mission payloads, communication links and ground control equipment selected for each projectProject-specific selection; final equipment list defined in the quotation. |
| Payload integration constraints | Installation depends on equipment dimensions, mounting requirements and final layoutFlight systems share the fuselage space with project equipment. |
| Communication range | Dependent on the selected data linkSelected data link. |
| Payload and fuel allocation | Payload and fuel must be selected together to meet endurance requirementsWithin the aircraft’s take-off weight limit. |
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